EP3067625B1 - Gasturbinenbrennkammer, gas turbine und verfahren - Google Patents
Gasturbinenbrennkammer, gas turbine und verfahren Download PDFInfo
- Publication number
- EP3067625B1 EP3067625B1 EP13896977.9A EP13896977A EP3067625B1 EP 3067625 B1 EP3067625 B1 EP 3067625B1 EP 13896977 A EP13896977 A EP 13896977A EP 3067625 B1 EP3067625 B1 EP 3067625B1
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- European Patent Office
- Prior art keywords
- fuel
- air
- plate
- air hole
- gas turbine
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Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00016—Retrofitting in general, e.g. to respect new regulations on pollution
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03042—Film cooled combustion chamber walls or domes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
Definitions
- the present invention relates to a gas turbine combustor.
- Combustors designed to reduce the NOx emission include those employing premix combustion.
- the premix combustion is a combustion method in which air-fuel mixture obtained by previously mixing fuel and air together (premixed gas) is supplied to the combustor and brought into combustion.
- a combustor of this type comprises a burner having a premixer and a combustion chamber arranged downstream of the burner in the flow direction of the air-fuel mixture.
- the premixer is a device for generating the air-fuel mixture.
- the air-fuel mixture is supplied from the premixer to the combustion chamber and combusts in the combustion chamber.
- the fuel and air are previously mixed together and supplied to the combustion chamber, by which the temperature of the flame formed in the combustion chamber is uniformized and the NOx emission from the combustor is reduced.
- the air temperature or the hydrogen content in the fuel increases, the combustion speed increases and the possibility of the so-called “flashback" (the flame formed in the combustion chamber flowing back to the premixer and so forth) arises.
- JP 2009 014324 A a combustion device and a gas turbine combustor are described.
- the combustion device comprises fuel injection nozzles and air fuel mixture injection nozzles for injecting first air fuel mixture composed by mixing the fuel with the primary air.
- a humid air turbine and fuel control method for said air turbine is described.
- the device includes a plural of combustion units with plural fuel nozzles for supplying fuel. Further, air nozzles are provided for supplying air for the combustion. A part of the plural combustion units are better in flame stabilizing performance than the other combustion units.
- a fuel ratio at which fuel is fed to the part of the combustion units is set on the basis of internal temperature of the humidification tower and internal pressure of the humidification tower to control a flow ratio of the fuel fed to the plural combustion units.
- JP4922878B2 discloses a configuration in which an air hole plate, including a first perforated plate formed with a plurality of first air holes and a second perforated plate formed with a plurality of second air holes, is arranged downstream of a plurality of fuel nozzles.
- the air-fuel mixture ejected from the first air holes is made to collide with the second perforated plate and is ejected into the combustion chamber through the second air holes.
- air is ejected also from first air holes to which no fuel is supplied.
- the air-fuel mixture ejected from part of the first air holes is diluted in the space between the first and second perforated plates by the air ejected from the other first air holes and the fuel-air ratio of the air-fuel mixture ejected into the combustion chamber through the second air holes can become excessively low. If the fuel-air ratio of the air-fuel mixture flowing into the second air holes cannot be precisely controlled as in this case, it is difficult to maintain stable combustion in a series of operation steps from the ignition of the gas turbine to the full load operation.
- the object of the present invention which has been made in consideration of the above-described situation, is to provide a combustor according to claim 1 capable of precisely controlling the fuel-air ratio in each air hole and thereby achieving stable combustion in a series of operation steps from the ignition of the gas turbine to the full load operation while also reducing the NOx emission.
- a combustor capable of precisely controlling the fuel-air ratio in each air hole and thereby achieving stable combustion in a series of operation steps from the ignition of the gas turbine to the full load operation while also reducing the NOx emission.
- Fig. 1 is a schematic diagram showing the overall configuration of a power generation gas turbine plant 1000 comprising the gas turbine combustor 2 according to this embodiment.
- the gas turbine plant 1000 comprises a gas turbine and a generator 20.
- the gas turbine includes a compressor 1, a gas turbine combustor 2 and a turbine 3.
- the compressor 1 compresses intake air 100 taken in through an intake part (unshown), thereby generates high-pressure air 101, and supplies the high-pressure air 101 to the gas turbine combustor 2.
- the gas turbine combustor 2 mixes the high-pressure air 101 supplied from the compressor 1 with the fuel supplied through a fuel system 200 (explained later), combusts the air-fuel mixture, thereby generates high-temperature combustion gas 102, and supplies the high-temperature combustion gas 102 to the turbine 3.
- the turbine 3 is driven by the expansion of the combustion gas 102 supplied from the gas turbine combustor 2.
- the generator 20 is rotated by the drive force obtained by the turbine 3 and generates electric power.
- the compressor 1, the turbine 3 and the generator 20 are linked together by an integral shaft 21. The drive force obtained by the driving of the turbine 3 is transmitted to the compressor 1 and the generator 20 via the shaft 21.
- the gas turbine combustor 2 comprises a burner 5, a combustor liner 10, a flow sleeve 11, an inner tail tube 12, an outer tail tube 13, fuel systems 201 - 204, and a header 40.
- the gas turbine combustor 2 is stored in the casing 4 of a gas turbine unit.
- the burner 5 is arranged in the gas turbine combustor 2.
- the combustor liner 10, formed in a cylindrical shape for separating the combustion gas 102 generated by the gas turbine combustor 2 from the high-pressure air 101 supplied from the compressor 1, is arranged inside the gas turbine combustor 2 and downstream of the burner 5 in the flow direction of the combustion gas 102.
- the flow sleeve 11 Arranged outside the combustor liner 10 is the flow sleeve 11 which is formed in a cylindrical shape to cover the combustor liner 10. An annular space formed between the combustor liner 10 and the flow sleeve 11 constitutes a channel 48 through which the high-pressure air 101 supplied from the compressor 1 to the gas turbine combustor 2 flows.
- the air-fuel mixture of the high-pressure air 101 ejected from the burner 5 and the fuel supplied through the fuel system 200 is combusted.
- One end of the combustor liner 10 farther from the burner 5 (downstream end in the flow direction of the combustion gas 102) is inserted into one end of the inner tail tube 12.
- the inner tail tube 12 is a tube for leading the combustion gas 102 generated in the combustion chamber 50 to the turbine 3.
- the other end of the inner tail tube 12 is connected to a line connecting the gas turbine combustor 2 and the turbine 3 together.
- the outer tail tube 13 Arranged outside the inner tail tube 12 is the outer tail tube 13 which is formed in a cylindrical shape to cover the inner tail tube 12.
- One end of the flow sleeve 11 farther from the burner 5 (downstream end in the flow direction of the combustion gas 102) is inserted into one end of the outer tail tube 13.
- the outer tail tube 13 forms an annular space between itself and the inner tail tube 12.
- the other end of the outer tail tube 13 is open to the inside of the casing 4.
- the space between the inner tail tube 12 and the outer tail tube 13 constitutes a channel 47 for the high-pressure air 101 flowing in from the other end of the outer tail tube 13.
- the high-pressure air 101 flowing into the channel 47 formed between the inner tail tube 12 and the outer tail tube 13 cools down the inner tail tube 12 from its outer surface by means of convection cooling. Further, the high-pressure air 101 flowing into the annular channel 48 formed between the flow sleeve 11 and the combustor liner 10 after flowing through the channel 47 is used for convection cooling of the combustor liner 10 arranged in the gas turbine combustor 2.
- the remaining high-pressure air 101 that was not used for the film cooling of the combustor liner 10 flows through the annular channel 48 and is supplied to the inside of the combustor liner 10 as combustion air via a great number of air holes 31 of the burner 5 provided for the gas turbine combustor 2. Then, via the great number of air holes 31, the combustion air is ejected from the burner 5 of the gas turbine combustor 2.
- the burner 5 is supplied with the fuel from four fuel systems 201 - 204 (F1 - F4 fuel systems).
- the F1 - F4 fuel systems 201 - 204 are provided with F1 - F4 fuel flow control valves 211 - 214, respectively.
- the fuel systems 201 - 204 branch out from the fuel system 200 having a fuel shut-off valve (switching valve) 210.
- the number of fuel systems branching out from the fuel system 200 is not limited to four.
- the fuel flowing through the fuel systems 201 - 204 is supplied to the header 40 which is partitioned into multiple rooms differing in the radial direction distance from the central axis of the combustor liner 10.
- the header 40 is partitioned into a first header 51, a second header 52, a third header 53 and a fourth header 54.
- the F1 fuel system 201, the F2 fuel system 202, the F3 fuel system 203 and the F4 fuel system 204 are connected to the first header 51, the second header 52, the third header 53 and the fourth header 54, respectively.
- the fuel supplied to the header 40 via each fuel system is injected from tip ends of fuel nozzles 30 supported by the header 40 and supplied to the burner 5.
- the number of partitioned spaces (rooms) in the header 40 is not limited to four.
- the flow rate of F1 fuel supplied to the burner 5 through the F1 fuel system 201 is regulated by the F1 fuel flow control valve 211.
- the flow rate of F2 fuel supplied to the burner 5 through the F2 fuel system 202 is regulated by the F2 fuel flow control valve 212.
- the flow rate of F3 fuel supplied to the burner 5 through the F3 fuel system 203 is regulated by the F3 fuel flow control valve 213.
- the flow rate of F4 fuel supplied to the burner 5 through the F4 fuel system 204 is regulated by the F4 fuel flow control valve 214.
- the amount of power generation by the gas turbine plant 1000 is controlled by regulating the flow rates of the F1 fuel, the F2 fuel, the F3 fuel and the F4 fuel with the fuel flow control valves 211, 212, 213 and 214, respectively.
- Fig. 2 is a partial structural drawing showing the structure around the burner 5 of the gas turbine combustor 2 according to this embodiment.
- the burner 5 includes a plurality of fuel nozzles 30, a base plate (first plate) 32, a turning plate (second plate) 33, and partition wall parts 37.
- each part of the burner 5 will be explained below.
- multiple rows of air holes (air hole rows) arranged concentrically will be referred to as a first row, a second row, ..., and an eighth row from inside to outside as needed.
- a plurality of fuel nozzles 30 for ejecting the fuel supplied from the fuel system 200 are supported by the fuel header 40.
- These fuel nozzles 30 are arranged in a plurality of (eight in this embodiment) concentric annular rows. In each annular row, the fuel nozzles 30 are formed around the whole circumference of the annular row.
- Fig. 5 is a schematic diagram of the base plate 32 in this embodiment viewed from the downstream side.
- the base plate 32 as a disc-shaped plate coaxial with the central axis of the combustor liner 10, is arranged downstream of the fuel nozzles 30 in the fuel flow direction.
- the base plate 32 is formed with a plurality of (eight in this embodiment) concentric circular air hole rows made up of the air holes 31A corresponding to the fuel nozzles 30, respectively, have been formed.
- each air hole 31A is arranged on the fuel ejection side of a corresponding fuel nozzle 30 in its axial direction (downstream side in the fuel ejection direction) in association with the corresponding fuel nozzle 30.
- each air hole 31A is formed in the shape of a right cylinder in which the two circles forming the end faces are orthogonal to the generating line, and arranged coaxially with the corresponding fuel nozzle 30.
- Each fuel nozzle 30 is not inserted into the corresponding air hole 31A, that is, the end face of the air hole 31A on the upstream side in the fuel flow direction (hereinafter referred to as an "inlet" as needed) is apart from the end of the fuel nozzle 30 on the downstream side in the fuel flow direction.
- the turning plate 33 is arranged downstream of the base plate 32 in the fuel flow direction to face the base plate 32.
- a plurality of concentric circular air hole rows made up of air holes 31B and corresponding to the plurality of (eight in this embodiment) air hole rows of the base plate 32 have been formed.
- These air holes 31B are formed around the whole circumference of each annular air hole row.
- the number of air holes 31B equals the number of air holes 31A of the base plate 32.
- Fig. 3 is an enlarged view of the turning plate 33 in this embodiment (cross-sectional view taken along the line III - III in Fig. 4).
- Fig. 4 is a schematic diagram of the turning plate 33 in this embodiment viewed from the downstream side.
- each air hole 31B is formed in the shape of an oblique cylinder in which the two ellipses forming the end faces are not orthogonal to the generating line.
- the air hole 31B is a turning air hole having a turning angle.
- the end of the air hole 31B on the downstream side in the flow direction of the air-fuel mixture (hereinafter referred to as an "outlet” as needed) is shifted from the position of the upstream end (hereinafter referred to as an "inlet” as needed) in the circumferential direction.
- the central axis of the air hole 31B (obtained by connecting the centers of two circles at both ends of the air hole 31B) is oblique to the turning plate 33 in the circumferential direction to have a prescribed angle ⁇ ° from the central axis of the fuel nozzle 30, the central axis of the air hole 31A, or the central axis of the combustor liner 10.
- the air hole 31B is oblique to the turning plate 33 in the circumferential direction by the prescribed angle ⁇ °.
- the expression "have a prescribed angle” in this embodiment means that the central axis of the air hole 31B is not parallel or orthogonal to the other central axis (the central axis of the fuel nozzle 30, the central axis of the air hole 31A, or the central axis of the combustor liner 10).
- the angle ⁇ ° is an element prescribing the air ejection direction from the air hole 31B.
- the angle ⁇ ° has been set at an optimum value in each air hole row of the air holes 31B.
- the base plate 32 and the turning plate 33 are attached to the fuel header 40 via a support 15.
- the base plate 32 and the turning plate 33 are held in the combustor liner 10 via a spring seal 14.
- the support 15 is in a shape formed by bending a flat plate. By forming the support 15 in such a shape, thermal expansion in the circumferential direction can be absorbed by the bent structure and the reliability of the burner 5 can be increased.
- the burner 5 constituting a combustion unit of the gas turbine combustor 2 is divided into multiple regions.
- four rows forming the innermost one of the regions constitute a first-group combustion unit (F1 burner) 5A
- the fifth row constitutes a second-group combustion unit (F2 burner) 5B
- the sixth row constitutes a third-group combustion unit (F3 burner) 5C
- two rows on the peripheral side constitute a fourth-group combustion unit (F4 burner) 5D.
- the F1 - F4 fuel systems 201 - 204 are connected to the F1 - F4 burners 5A - 5D via the aforementioned first through fourth headers 51 - 54, respectively.
- Such a group structure with the fuel systems 201 - 204 branching out from the fuel system 200 makes it possible to carry out the so-called “fuel staging” (changing the number of fuel nozzles 30 used for the fuel supply in stages in response to the change in the fuel flow rate required by the gas turbine).
- the gap formed between two air holes 31B adjoining each other in the circumferential direction has been set greater than the flame quenching distance. With this setting, the flame approaches the turning plate 33 and the stability of the flame is enhanced.
- the gap formed between two air holes 31B adjoining each other in the circumferential direction has been set less than or equal to the flame quenching distance, by which the flame is formed apart from the turning plate 33.
- the mixing of the fuel jet 34 and the air jet 35 progresses rapidly when the channel suddenly enlarges from the air holes 31B to the combustion chamber 50. If the flame is formed at a position apart downstream from the turning plate 33, low NOx combustion can be performed since premixed gas of fuel and air sufficiently mixed together reaches the flame and combusts.
- the first combustion unit F1 and the second through fourth combustion units F2 - F4 have different functions; the first combustion unit F1 has the function of enhancing stable combustion while the second combustion unit F2, the third combustion unit F3 and the fourth combustion unit F4 have the function of performing low NOx combustion.
- the base plate 32 in this embodiment is provided with the partition wall parts 37 which partition a space part 46 formed between the base plate 32 and the turning plate 33 into rooms corresponding to the air hole rows of the base plate 32 and the turning plate 33.
- the space part 46 exists between the base plate 32 and the turning plate 33 (see Fig. 2 , for example).
- the periphery of the space part 46 is covered by a burner partition wall 49.
- the space part 46 connects with the end of each air hole 31A of the base plate 32 on the downstream side in the flow direction of the air-fuel mixture (hereinafter referred to as an "outlet" as needed) and the inlet of each air hole 31B.
- the air holes 31A and the air holes 31B are connected with each other via the space part 46.
- only the air-fuel mixture of the fuel jet 34 and the air jet 35 ejected from the air holes 31A flows through the space part 46 covered by the burner partition wall 49; there is no inflow of secondary fuel, secondary air, etc. into the space part 46 covered by the burner partition wall 49.
- the partition wall parts 37 are formed concentrically corresponding to the air hole rows made up of the air holes 31A.
- Each partition wall part 37 extends from the base plate 32 to the turning plate 33 and contacts the opposing surface of the turning plate 33 (see Fig. 2 ).
- the space part 46 is partitioned into a plurality of annular internal channels 36 (eight internal channels 36 in this embodiment). These internal channels 36 are formed in a concentric circular pattern.
- Fig. 6 is an enlarged view of the region surrounded by dotted lines in Fig. 5 .
- Fig. 7 is a perspective view of the VII - VII cross section in Fig. 6 .
- the width W36 of each internal channel 36 (dimension of the internal channel 36 in the radial direction of the base plate 32) has been set at a dimension greater than or equal to the hole diameter of the air hole 31A.
- the depth D36 of each internal channel 36 with reference to the plane where the partition wall parts 37 contact the turning plate 33 has been set at a dimension equivalent to the hole diameter of the air hole 31A.
- S31 represent the cross-sectional area of the air hole 31A (one air hole 31A), the width W36 and the depth D36 of the internal channel 36 are, according to a preferred embodiment of the invention, desired to be set to satisfy the following expression (1): S 31 ⁇ W 36 ⁇ D 36
- the expression (1) indicates that the cross-sectional area of the internal channel 36 is greater than or equal to that of the air hole 31A.
- width W36 and the depth D36 of the internal channel 36 are set to satisfy S31 > W36 ⁇ D36 contrary to the expression (1), the flow velocity in the internal channel 36 increases and the mixing of fuel and air is promoted; however, the efficiency of the gas turbine plant 1000 can drop due to an increase in the pressure loss.
- the width W36 and the depth D36 of the internal channel 36 are set greater than the hole diameter of the air hole 31A, a non-stationary vortex or stagnation can locally occur in the internal channel 36 and deteriorate the reliability of the combustor. Therefore, the width W36 and the depth D36 of the internal channel 36 are desired to be set to satisfy the following expression (2) : 2 ⁇ S 31 > W 36 ⁇ D 36
- Fig. 8 is a cross-sectional view schematically showing the flow of fuel and air in the burner 5 in this embodiment (cross-sectional view taken along the line VIII - VIII in Fig. 6 ).
- the high-pressure air 101 which has been led to the combustion chamber 50 via the channels 47 and 48 flows into the air holes 31A formed through the base plate 32 of the air hole plate 39 as the air jets 35.
- the fuel which has been supplied from the fuel system 200 to the fuel nozzles 30 via the fuel header 40 is ejected from the discharge holes of the fuel nozzles 30 and flows into the air holes 31A as the fuel jets 34.
- Each fuel jet 34 flowing into the air hole 31A is surrounded and covered by the air jet 35, flows downstream from the air hole 31A to an internal channel 36 of the space part 46, and fills the internal channel 36. Since the degree of mixing of the air-fuel mixture jet of the fuel jet 34 and the air jet 35 is still low, the fuel concentration is high in the central part and low in the peripheral part.
- the temperature of the fuel jet 34 is several hundred °C lower than that of the air jet 35, and thus the temperature of the air-fuel mixture jet ejected from the air hole 31A is low in the central part and high in the peripheral part.
- the channel for the jet suddenly enlarges and the mixing is promoted in the vicinity of the inlet of the internal channel 36 (outlet of the air hole 31A) (primary mixing).
- the air-fuel mixture of the fuel jet 34 and the air jet 35 formed by the primary mixing flows from the internal channel 36 into an air hole 31B formed through the turning plate 33.
- the primary air-fuel mixture flows into the air hole 31B, the channel size suddenly reduces and the mixing is promoted further in the vicinity of the inlet of the air hole 31B (outlet of the internal channel 36) (secondary mixing).
- the air-fuel mixture of the fuel jet 34 and the air jet 35 formed by the secondary mixing flows through the air hole 31B. Since the air hole 31B is formed as a path inclined at the angle ⁇ ° (oblique cylindrical path), a force component in a turning direction is given to the secondary air-fuel mixture flowing through the air hole 31B and a circulating flow is formed. Since the outlet of the air hole 31B is open to the combustion chamber 50, the channel for the secondary air-fuel mixture suddenly enlarges and the mixing is promoted further in the vicinity of the outlet of the air hole 31B (tertiary mixing).
- the air-fuel mixture of the fuel jet 34 and the air jet 35 formed by the tertiary mixing (tertiary air-fuel mixture) is ejected into the combustion chamber 50 as premixed gas 38 while turning and is combusted in the combustion chamber 50.
- Fig. 9 is a schematic diagram showing the fuel staging in the gas turbine combustor 2 according to this embodiment.
- the horizontal axis represents the elapsed time and the vertical axis represents the fuel flow rate.
- the fuel is supplied from the fuel system 200 to the F1 burner 5A, the F2 burner 5B and the F3 burner 5C, whereas the F4 burner 5D is supplied with no fuel.
- the operation is switched to solo combustion of the F1 burner 5A and the turbine 3 is accelerated until the turbine 3 reaches the rated revolution speed no load state (FSNL: Full Speed No Load).
- FSNL Full Speed No Load
- only the F1 burner 5A is supplied with the fuel from the fuel system 200.
- the F2 burner 5B, the F3 burner 5C and the F4 burner 5D are supplied with no fuel.
- the power generation is started and the load is increased gradually.
- the fuel supply range area
- the fuel is successively supplied in the order of the F2 burner 5B, the F3 burner 5C and the F4 burner 5D) so that the fuel-air ratio of the burner 5 of the gas turbine combustor 2 remains in a stable combustion range.
- the rated revolution speed full load state (FSFL: Full Speed Full Load) is achieved.
- the downstream ends of the fuel nozzles 30 in the fuel flow direction are apart from the inlets of the air holes 31A. Therefore, the increase in the flow velocity of the fuel in the air hole 31A can be suppressed and the drop in the efficiency of the gas turbine plant 1000 due to the increase in the pressure loss can be reduced in comparison with a configuration in which the tip ends of the fuel nozzles 30 are inserted into the air holes 31A, for example.
- the fuel jet 34 and the air jet 35 are ejected into the combustion chamber 50 in the form of a coaxial jet, by which the interfacial area between the fuel and air is increased and the mixing of the fuel and air is promoted further. Accordingly, the amount of NOx generated by the combustion in the combustion chamber 50 can be reduced.
- the fluid flowing through the air holes 31B is injected from the air holes 31B while forming a circulating flow. Accordingly, flame with higher stability can be formed.
- the gas turbine combustor is formed in simple structure in which the turning plate 33 having the air hole rows corresponding to the air hole rows of the base plate 32 is arranged downstream of the base plate 32 and the partition wall parts 37 are arranged to partition the space part 46 between the base plate 32 and the turning plate 33 into rooms corresponding to the air hole rows. Therefore, the gas turbine combustor can be manufactured with ease by modifying an existing gas turbine combustor.
- the present invention is easily applicable to an existing gas turbine combustor comprising: a combustion chamber in which fuel is burned with air to generate combustion gas; a plurality of fuel nozzles arranged in multiple concentric annular rows; and a base plate arranged downstream of the fuel nozzles and having multiple concentric circular air hole rows made up of a plurality of air holes corresponding to the fuel nozzles, by arranging the turning plate 33 downstream of the base plate and arranging the partition wall parts 37 in the space part between the base plate and the turning plate 33.
- Fig. 10 is a cross-sectional view schematically showing the flow of fuel and air in a gas turbine combustor according to this embodiment. Elements in Fig. 10 equivalent to those in the above-described first embodiment are assigned the already-used reference characters and repeated explanation thereof is appropriately omitted.
- This embodiment differs from the first embodiment in the configuration of the air holes 31B of the turning plate 33.
- the configuration of the air holes 31B will be explained below.
- the air holes 31B in the first embodiment are formed at positions corresponding to the air holes 31A in the circumferential direction
- the air holes 31B in this embodiment are formed as shown in Fig. 10 .
- the inlets of the air holes 31B of the turning plate 33 connecting to the space part 46 and the outlets of the air holes 31A connecting to the space part 46 are shifted from each other in the circumferential direction.
- the intersection point between the central axis of each air hole 31B and the surface of the turning plate 33 on the fuel nozzle 30's side i.e., the center of the inlet of the air hole 31B
- a wall surface of the turning plate 33 is situated on the central axis of each air hole 31A.
- the rest of the configuration is equivalent to that in the first embodiment.
- the fuel jet 34 ejected from the fuel nozzle 30 and the air jet 35 form the primary air-fuel mixture in the internal channel 36 similarly to the first embodiment.
- the primary air-fuel mixture collides with the wall surface of the turning plate 33 situated on the central axis of the air hole 31A and then flows in the circumferential direction along the internal channel 36. Thereafter, the primary air-fuel mixture flows into an air hole 31B and is supplied to the combustion chamber 50 as the premixed gas 38 and combusted similarly to the first embodiment.
- the outlets of the air holes 31A and the inlets of the air holes 31B are shifted from each other in the circumferential direction and a wall surface of the turning plate 33 is situated on the central axis of each air hole 31A. Accordingly, the air-fuel mixture jet ejected from the air hole 31A with a low-temperature part existing at the center of the jet collides with the wall surface. Thus, the turning plate 33 heated by the thermal radiation from the flame in the combustion chamber 50 can be cooled down and the operating life of the turning plate 33 can be increased.
- the distance for which the air-fuel mixture jet flows in the internal channel 36 (hereinafter referred to as a "mixing distance") can be made longer than that in the first embodiment. Therefore, the mixing of fuel and air in the internal channel 36 can be promoted further and the NOx emission can be reduced further.
- Fig. 11 is a schematic diagram of a base plate of a gas turbine combustor according to this embodiment viewed from the downstream side.
- Fig. 12 is an enlarged view of the base plate of the gas turbine combustor according to this embodiment (cross-sectional view taken along the line XII - XII in Fig. 11 ).
- Fig. 13 is a cross-sectional view schematically showing the flow of fuel and air in the gas turbine combustor according to this embodiment. Elements in Figs. 11 - 13 equivalent to those in the first embodiment are assigned the already-used reference characters and repeated explanation thereof is appropriately omitted.
- This embodiment differs from the above-described embodiments in the configuration of the air holes 31A.
- the central axis of the air hole 31A of the base plate 32 (obtained by connecting the centers of the two circles at both ends of the air hole 31A) extends obliquely with respect to the circumferential direction of the base plate 32 to have a prescribed angle ⁇ ° from the central axis of the fuel nozzle 30 or the central axis of the combustor liner 10.
- the air hole 31A is formed to be oblique to the base plate 32 by the prescribed angle ⁇ °.
- the expression "have a prescribed angle” in this embodiment means that the central axis of the air hole 31A is not parallel to the other central axis (the central axis of the fuel nozzle 30 or the central axis of the combustor liner 10).
- the angle ⁇ ° is an element prescribing the air ejection direction from the air hole 31A into the internal channel 36.
- the angle ⁇ ° has been set at an optimum value in each air hole row of the air holes 31A.
- the air hole 31A is formed as a path inclined at the angle ⁇ ° (oblique cylindrical path).
- the rest of the configuration e.g., a wall surface of the turning plate 33 being situated on the central axis of each air hole 31A) is equivalent to that in the second embodiment.
- the fuel jet 34 ejected from the fuel nozzle 30 and the air jet 35 form the primary air-fuel mixture in the internal channel 36 similarly to the first embodiment and then collide with the wall surface of the turning plate 33 situated on the central axis of the air hole 31A. Since the air hole 31A is formed obliquely to the base plate 32 in this embodiment, the primary air-fuel mixture flows in the internal channel 36 in one direction (circumferential direction) in an orderly manner while colliding with the wall surface of the turning plate 33 and then flows into an air hole 31B. Thereafter, the air-fuel mixture is supplied to the combustion chamber 50 as the premixed gas 38 and combusted similarly to the first embodiment.
- each air hole 31A formed through the base plate 32 is inclined from the axial direction of the fuel nozzle 30 or the combustor liner 10 in the circumferential direction of the base plate 32. Therefore, a force component in a turning direction is actively given to the air-fuel mixture jet flowing through the air hole 31A. Accordingly, the primary air-fuel mixture in the internal channel 36 flows in one direction (circumferential direction of the internal channel 36) in an orderly manner while colliding with the wall surface of the turning plate 33. Consequently, the occurrence of a local vortex or stagnation to the primary air-fuel mixture in the internal channel 36 can be suppressed, the pressure loss occurring when the air-fuel mixture flows through the internal channel 36 can be reduced, and the mixing of fuel and air can be promoted.
- Fig. 14 is a cross-sectional view schematically showing the flow of fuel and air in a gas turbine combustor according to this embodiment. Elements in Fig. 14 equivalent to those in the first embodiment are assigned the already-used reference characters and repeated explanation thereof is appropriately omitted.
- This embodiment differs from the above-described embodiments in that the air hole 31B of the turning plate 33 is provided with a restrictor.
- a step-like restrictor 39A is formed on the inlet side (fuel nozzle 30's side) of the air hole 31B formed through the turning plate 33.
- the restrictor 39A is formed so that the hole diameter of the air hole 31B decreases on the inlet side of the air hole 31B. As a result, the area of the inlet of the air hole 31B is decreased compared to the third embodiment, for example.
- the intersection point between the central axis of each air hole 31B and the surface of the turning plate 33 on the fuel nozzle 30's side is apart from the central axis of the corresponding air hole 31A in the circumferential direction, and a wall surface of the turning plate 33 is situated on the central axis of each air hole 31A.
- the rest of the configuration is equivalent to that in the second embodiment.
- the fuel jet 34 ejected from the fuel nozzle 30 and the air jet 35 form the primary air-fuel mixture in the internal channel 36 similarly to the first embodiment.
- the primary air-fuel mixture collides with a wall surface of the turning plate 33 (situated on the central axis of the air hole 31A) while flowing in the internal channel 36 in the circumferential direction.
- the hole diameter of the air hole 31B on the fuel nozzle 30's side is reduced by forming the restrictor 39A on the inlet side of the air hole 31B.
- the primary air-fuel mixture flowing in the internal channel 36 in the circumferential direction flows from the internal channel 36 into an air hole 31B of the turning plate 33, the primary air-fuel mixture is distributed to the air holes 31B of the same row more evenly compared to the first embodiment. Thereafter, the primary air-fuel mixture flows into the air holes 31B and is supplied to the combustion chamber 50 as the premixed gas 38 and combusted similarly to the first embodiment.
- the restrictor 39A is formed on the inlet side of the air hole 31B and the hole diameter of the air hole 31B is reduced. Therefore, the circumferential deviation in the flow rate of the premixed gas 38 injected from each air hole 31B into the combustion chamber 50 (flow rate deviation among the air holes) can be reduced further. Additionally, the mixing of fuel and air can be promoted further since the channel suddenly enlarges downstream of the restrictor 39A.
- Fig. 15 is a cross-sectional view schematically showing the flow of fuel and air in a gas turbine combustor according to this embodiment. Elements in Fig. 15 equivalent to those in the first embodiment are assigned the already-used reference characters and repeated explanation thereof is appropriately omitted.
- This embodiment illustrates another example of the configuration of the restrictor formed in the air hole 31B of the turning plate 33.
- a slope-like restrictor 39B is formed on the inlet side (fuel nozzle 30's side) of the air hole 31B of the turning plate 33 so that the hole diameter gradually decreases from the outlet side (combustion chamber 50's side) toward the inlet side of the air hole 31B.
- the restrictor 39B is formed so that the hole diameter of the air hole 31B hits the minimum at the end on the fuel nozzle 30's side. As a result, the area of the inlet of the air hole 31B is decreased compared to the third embodiment, for example.
- the intersection point between the central axis of each air hole 31B and the surface of the turning plate 33 on the fuel nozzle 30's side is apart from the central axis of the corresponding air hole 31A in the circumferential direction, and a wall surface of the turning plate 33 is situated on the central axis of each air hole 31A.
- the rest of the configuration is equivalent to that in the second embodiment.
- the fuel jet 34 ejected from the fuel nozzle 30 and the air jet 35 form the primary air-fuel mixture in the internal channel 36 similarly to the first embodiment.
- the primary air-fuel mixture collides with a wall surface of the turning plate 33 (situated on the central axis of the air hole 31A) while flowing in the internal channel 36 in the circumferential direction. Since a restrictor (restrictor 39B) is formed on the inlet side of the air hole 31B also in this embodiment, the primary air-fuel mixture flowing in the internal channel 36 in the circumferential direction is distributed to the air holes 31B of the same row more evenly compared to the first embodiment similarly to the fourth embodiment. Thereafter, the primary air-fuel mixture flows into the air holes 31B and is supplied to the combustion chamber 50 as the premixed gas 38 and combusted similarly to the first embodiment.
- the slope-like restrictor 39B is formed on the inlet side (fuel nozzle 30's side) of the air hole 31B of the turning plate 33 so that the hole diameter gradually decreases from the outlet side (combustion chamber 50's side) toward the inlet side of the air hole 31B. Since the air hole 31B is formed in a tapered shape with no step, the increase in the pressure loss caused by the sudden enlargement of the channel when the air-fuel mixture flows from the internal channel 36 into the air hole 31B can be suppressed compared to the fourth embodiment and the efficiency of the gas turbine plant 1000 can be increased.
- Fig. 16 is a cross-sectional view of a gas turbine combustor according to this embodiment.
- Fig. 17 is a schematic diagram of an air hole plate of the gas turbine combustor according to this embodiment viewed from the downstream side (cross-sectional view taken along the line XVII - XVII in Fig. 16 ).
- Elements in Figs. 16 and 17 equivalent to those in the first embodiment are assigned the already-used reference characters and repeated explanation thereof is appropriately omitted.
- the present invention is applied to the so-called multiple injection gas turbine combustor in which a plurality of burners, each including a plurality of fuel nozzles and multiple air hole rows made up of air holes are arranged in a concentric circular pattern, are arranged in a combustion unit of the gas turbine combustor.
- the concentrically arranged air hole rows will be referred to as the first row, the second row and the third row from the center toward the periphery as needed.
- the gas turbine combustor 2 comprises a plurality of burners in each of which a plurality of fuel nozzles 30 and multiple air hole rows made up of a plurality of air holes 31A and 31B are arranged in a concentric circular pattern (three rows of fuel nozzles 30 and three air hole rows in this embodiment).
- a plurality of fuel nozzles 30 and multiple air hole rows made up of a plurality of air holes 31A and 31B are arranged in a concentric circular pattern (three rows of fuel nozzles 30 and three air hole rows in this embodiment).
- six fuel nozzles 30 and air holes 31A and 31B are arranged in the first row
- twelve fuel nozzles 30 and air holes 31A and 31B are arranged in the second row
- eighteen fuel nozzles 30 and air holes 31A and 31B are arranged in the third row.
- one burner (pilot burner) 41 is arranged coaxially with the gas turbine combustor 2 and six burners (main burners) 42 are arranged around the pilot burner 41.
- the gas turbine combustor 2 in this embodiment is configured as a multi-burner structure including seven burners.
- the seven burners 41 and 42 share a base plate 32 and a turning plate 33.
- the turning plate 33 of the burners 41 and 42 is provided with the air holes 31A and 31B, the partition wall parts 37, etc. of each embodiment described above.
- Fig. 18 is an enlarged view of a part of the turning plate 33 surrounded by the chain lines (part A) in Fig. 16 .
- Fig. 19 is an enlarged view of the main burner 42 surrounded by the chain line (part B) in Fig. 17 .
- multiple partition wall parts 37 are formed in a concentric circular pattern so as to separate the air hole rows (made up of a plurality of air holes 31A and 31B) from each other (in this embodiment, two partition wall parts 37 are formed in each burner 41/42).
- the space part 46 of the turning plate 33 is partitioned into multiple internal channels 36 for leading the air-fuel mixture (ejected from the air holes 31A) in the circumferential direction (in this embodiment, the space part 46 in each burner 41/42 is partitioned into three internal channels 36).
- the internal channels 36 are formed in a concentric circular pattern corresponding to the partition wall parts 37.
- the air hole 31B is formed as a turning air hole having a turning angle as shown in Fig. 18 .
- the fuel is supplied from a fuel system 200 having a fuel shut-off valve 210 to the pilot burner 41 and the main burners 42 via a header 40.
- the fuel system 200 branches into four fuel systems: an F1 fuel system 201 having an F1 fuel flow control valve 211; an F2 fuel system 202 having an F2 fuel flow control valve 212; an F3 fuel system 203 having an F3 fuel flow control valve 213; and an F4 fuel system 204 having an F4 fuel flow control valve 214.
- the F1 fuel system 201 is connected to an F1 burner 43 constituting the pilot burner 41.
- the flow rate of F1 fuel supplied to the F1 burner 43 is regulated by the F1 fuel flow control valve 211.
- the F2 fuel system 202 is connected to an F2 burner 44 constituting the first rows of two main burners 42 in the six main burners 42.
- the flow rate of F2 fuel supplied to the F2 burner 44 is regulated by the F2 fuel flow control valve 212.
- the F3 fuel system 203 is connected to an F3 burner 45 constituting the first rows of the remaining four main burners 42 in the six main burners 42.
- the flow rate of F3 fuel supplied to the F3 burner 45 is regulated by the F3 fuel flow control valve 213.
- the F4 fuel system 204 is connected to an F4 burner 46 constituting the second and third rows of the six main burners 42.
- the flow rate of F4 fuel supplied to the F4 burner 46 is regulated by the F4 fuel flow control valve 214.
- partition wall parts 37 are formed in every burner (pilot burner 41, main burner 42) in this embodiment, it is sufficient if the partition wall parts 37 are formed only in burners that are required to perform the mixing of fuel and air with high accuracy. For example, it is possible to form the partition wall parts 37 only in the main burners 42 without forming the partition wall parts 37 in the pilot burner 41.
- the fuel jets 34 injected from the fuel nozzles 30 and the air jets 35 flowing into the gas turbine combustor 2 flow into the air holes 31A of each burner and then flow through the internal channels 36 and the air holes 31B in this order similarly to the first embodiment.
- the air-fuel mixture is ejected from the air holes 31B of each burner while forming a swirl flow 60 and is supplied to the combustion chamber 50 as the premixed gas 38.
- the premixed gas 38 is ejected from the air holes 31B of each burner while forming the swirl flow 60. Due to the swirl flow 60, a circulating flow 61 is formed at each burner and flame surfaces 62 are formed in the combustion chamber 50.
- the staging is performed and the fuel injection range (area) is enlarged in stages as explained in the first embodiment.
- the present invention is applicable also to the multiple injection gas turbine combustors with no problems.
- each fuel nozzle 30 and the air holes 31A are arranged coaxially with each other in the above embodiments, the central axes of the fuel nozzles 30 and the central axes of the air holes 31A do not need to perfectly coincide with each other as long as coaxial jets of fuel and air can be formed. It is sufficient if each fuel nozzle 30 extends toward or points the corresponding air hole 31A.
- the essential effects of the present invention are precisely controlling the fuel-air ratio of each air hole and thereby achieving stable combustion in a series of operation steps from the ignition of the gas turbine to the full load operation while also reducing the NOx emission. Therefore, it is not absolutely necessary to form the fuel nozzles 30, the air holes 31A and the air holes 31B around the whole circumference of each annular row as long as the essential effects are achieved. For example, there are cases where the fuel nozzles 30, the air holes 31A and the air holes 31B are arranged in part of an annular row in the peripheral part.
- the number of air hole rows formed through the base plate 32 and the turning plate 33 is not limited to eight as long as the aforementioned essential effects of the present invention are achieved.
- the number of air hole rows formed through the base plate 32 and the turning plate 33 can be seven or less, or nine or more.
- the numbers of the air holes 31A of the base plate 32 and the number of the air holes 31B of the turning plate 33 are equal to each other in the above embodiments, the numbers of the air holes 31A and 31B do not necessarily have to be set equal to each other as long as the aforementioned essential effects of the present invention are achieved.
- the number of the air holes 31B may be set larger than that of the air holes 31A, or smaller than that of the air holes 31A
- the tip ends of the fuel nozzles 30 are apart from the inlets of the air holes 31A of the base plate 32 in the above embodiments, the tip ends of the fuel nozzles 30 do not necessarily have to be arranged apart from the inlets of the air holes 31A as long as the aforementioned essential effects of the present invention are achieved.
- the tip ends of the fuel nozzles 30 may also be inserted into the air holes 31A. In this case, the mixing of the fuel ejected from each fuel nozzle 30 and the air is promoted further thanks to an increase in the flow velocity of the air jet 35 caused by a decrease in the inlet area of the air hole 31A.
- each fuel nozzle 30 is formed in a simple cylindrical shape in the above embodiments, it is also possible to arrange a protrusion at the tip end of each fuel nozzle 30 to cause a vortical flow in the fuel ejected and thereby further promote the mixing of fuel and air as long as the aforementioned essential effects of the present invention are achieved.
- the fuel nozzle 30 may also be formed to have two or more fuel ejection holes so as to enhance the dispersion of the fuel and thereby further promote the mixing of fuel and air.
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Claims (8)
- Gasturbinenverbrennungsvorrichtung (2), die Folgendes umfasst:eine Brennkammer (50), in der Brennstoff mit Luft verbrannt wird, um Verbrennungsgas zu erzeugen;mehrere Brennstoffdüsen (30), die in mehreren konzentrischen, ringförmigen Reihen angeordnet sind;eine erste Platte (32), die stromabwärts der Brennstoffdüsen (30) angeordnet ist und mehrere konzentrische, kreisförmige Luftlochreihen, die aus mehreren Luftlöchern, die den Brennstoffdüsen (30) entsprechen, gebildet sind, aufweist;eine zweite Platte (33), die stromabwärts der ersten Platte und der ersten Platte (32) zugewandt angeordnet ist und mehrere Luftlochreihen, die den Luftlochreihen der ersten Platte (32) entsprechen, aufweist, wobei die Luftlochreihen der zweiten Platte (33) aus mehreren Luftlöchern gebildet sind und ein Auslass jedes Luftlochs der zweiten Platte (33) zur Brennkammer (50) offen ist; undTrennwandteile (37), die entsprechend den Luftlochreihen der ersten Platte (32) und der zweiten Platte (33) konzentrisch ausgebildet sind, von der ersten Platte (32) zur zweiten Platte (33) verlaufen und die gegenüberliegende Oberfläche der zweiten Platte (33) kontaktieren, wobei die Trennwandteile (37) einen Raumteil (46) zwischen der ersten Platte (32) und der zweiten Platte (33) in mehrere ringförmige interne Innenkanäle (36), die den Luftlochreihen entsprechen, unterteilen.
- Gasturbinenverbrennungsvorrichtung (2) nach Anspruch 1, wobei die Positionen von Auslässen der Luftlöcher der ersten Platte (32) und die Positionen von Einlässen der Luftlöcher der zweiten Platte (33) zueinander in einer Umfangsrichtung verschoben sind.
- Gasturbinenverbrennungsvorrichtung (2) nach Anspruch 1, wobei die Luftlöcher der ersten Platte (32) von der Achsenrichtung einer Verbrennungsvorrichtungsauskleidung (10) in einer Umfangsrichtung der ersten Platte (32) geneigt sind.
- Gasturbinenverbrennungsvorrichtung (2) nach Anspruch 1, wobei die Querschnittsfläche eines Kanals der mehreren ringförmigen Innenkanäle (36), die im Raumteil (46) durch das Unterteilen durch die Trennwandteile (37) gebildet sind, wobei die Querschnittsfläche die Fläche des Kanalquerschnitts, der in radialer Richtung der ersten Platte (32) und der Tiefe (D36) des Kanals verläuft, ist, größer oder gleich der Querschnittsfläche eines Luftlochs der ersten Platte (32) ist.
- Gasturbinenverbrennungsvorrichtung (2) nach Anspruch 1, die Folgendes umfasst:mehrere Brennstoffkopfteile (40), die jeweils mit mehreren Bereichen, die durch Unterteilen der ringförmigen Reihen der Brennstoffdüsen (30) in einer radialen Richtung erhalten werden, verbunden sind; undmehrere Brennstoffsysteme (201-204), die jeweils mit den mehreren Brennstoffkopfteilen (40) verbunden sind.
- Gasturbinenverbrennungsvorrichtung (2) nach Anspruch 1, wobei das Luftloch der zweiten Platte (33) mit einem Durchflussregulierer (39A) versehen ist.
- Gasturbine, die Folgendes umfasst:eine Gasturbinenverbrennungsvorrichtung (2) nach Anspruch 1;einen Kompressor (1), der komprimierte Luft, die der Gasturbinenverbrennungsvorrichtung (2) zugeführt werden soll, erzeugt; undeine Turbine, die durch Verbrennungsgas, das von der Gasturbinenverbrennungsvorrichtung (2) zugeführt wird, angetrieben wird.
- Verfahren zum Modifizieren einer Gasturbinenverbrennungsvorrichtung (2), die eine Brennkammer (50), in der Brennstoff mit Luft verbrannt wird, um Verbrennungsgas zu erzeugen, mehrere Brennstoffdüsen (30), die in mehreren konzentrischen, ringförmigen Reihen angeordnet sind, und eine erste Platte (32), die stromabwärts der Brennstoffdüsen (30) angeordnet ist und mehrere konzentrische, kreisförmige Luftlochreihen, die aus mehreren Luftlöchern, die den Brennstoffdüsen (30) entsprechen, gebildet sind, aufweist, enthält, das die folgenden Schritte umfasst:Hinzufügen einer zweiten Platte (33), die stromabwärts der ersten Platte (32) und der ersten Platte zugewandt angeordnet ist und mehrere Luftlochreihen, die den Luftlochreihen der ersten Platte (32) entsprechen, aufweist, wobei die Luftlochreihen der zweiten Platte (33) aus mehreren Luftlöchern gebildet sind und ein Auslass jedes Luftlochs der zweiten Platte (33) zur Brennkammer (50) offen ist; undHinzufügen von Trennwandteilen (37), die entsprechend den Luftlochreihen der ersten Platte (32) und der zweiten Platte (33) konzentrisch gebildet sind, von der ersten Platte (32) zur zweiten Platte (33) verlaufen und die gegenüberliegende Oberfläche der zweiten Platte (33) kontaktieren, wobei die Trennwandteile (37) einen Raumteil (46) zwischen der ersten Platte und der zweiten Platte in mehrere ringförmige interne Innenkanäle, die den Luftlochreihen entsprechen, unterteilen.
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WO2015182727A1 (ja) * | 2014-05-30 | 2015-12-03 | 川崎重工業株式会社 | ガスタービンエンジンの燃焼装置 |
US10288292B2 (en) * | 2016-01-15 | 2019-05-14 | Delavan Inc | Swirlers |
EP3637000A1 (de) * | 2018-10-11 | 2020-04-15 | Siemens Aktiengesellschaft | Gasturbinenbrenner für reaktive Brennstoffe |
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JP7245150B2 (ja) * | 2019-12-16 | 2023-03-23 | 三菱重工業株式会社 | ガスタービン燃焼器 |
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- 2013-11-05 US US14/778,031 patent/US10018359B2/en active Active
- 2013-11-05 CN CN201380074801.6A patent/CN105074339B/zh active Active
- 2013-11-05 JP JP2015546181A patent/JP5940227B2/ja active Active
- 2013-11-05 WO PCT/JP2013/079943 patent/WO2015068212A1/ja active Application Filing
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Also Published As
Publication number | Publication date |
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CN105074339B (zh) | 2017-03-22 |
JP5940227B2 (ja) | 2016-06-29 |
CN105074339A (zh) | 2015-11-18 |
WO2015068212A1 (ja) | 2015-05-14 |
JPWO2015068212A1 (ja) | 2017-03-09 |
EP3067625A4 (de) | 2017-07-12 |
EP3067625A1 (de) | 2016-09-14 |
US10018359B2 (en) | 2018-07-10 |
US20160290646A1 (en) | 2016-10-06 |
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